Hypersonic vehicle design method and system
A technology of hypersonic speed and design method, which is applied in the direction of aircraft, supersonic aircraft, aircraft parts, etc., can solve the problems of small air flow capture area, insufficient capture flow, and small volume ratio, so as to improve loading efficiency and increase The effect of gas volume and internal resistance reduction
Active Publication Date: 2020-08-11
NAT UNIV OF DEFENSE TECH
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[0003] The present invention provides a hypersonic aircraft design method and system, which are used to overcome the defects of conventional hypersonic aircraft in the prior art, such as small volume ratio, large internal resistance, small air flow capture area, and insufficient capture flow, and improve the efficiency of hypersonic aircraft. The volume ratio, air capture flow rate, etc., make the large-volume hypersonic cargo flight tend to be feasible and practical
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[0033] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0034] In addition, the technical solutions of the various embodiments of the present invention can be combined with each other, but it must be based on the realization of those skilled in the art. When the combination of technical solutions is contradictory or cannot be realized, it should be considered as a combination of technical solutions. Does not exist, nor is it within the scope of protection required by the present invention.
[0035] This em...
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The invention discloses a hypersonic aircraft design method and system. The design method comprises the following steps: firstly, solving an inward turning type axisymmetric reference flow field through a swirling feature line theory, and generating parallel inward turning type air inlet channels in the reference flow field; then, designing a minimum resistance revolved body fuselage according tothe given length l and the turning radius d; designing a riding wing according to a lift-drag ratio requirement; and finally combining the parallel inward turning type air inlet channels, the minimumresistance revolved body fuselage and the riding wing, adopting an externally-hung mode to arrange an engine, and generating an integrated hypersonic aircraft with the parallel inward turning type airinlet channels + the minimum resistance revolved body fuselage + the riding wing. The hypersonic aircraft designed in the invention is large in volume and high in volume efficiency, so that the use of a large S-bending isolation section is avoided, and the internal resistance of the hypersonic aircraft designed by the method in the invention is obviously reduced compared with that of the conventional engine, the engine is externally hung, such that the space of the engine body is not occupied, and the loading efficiency of the internal volume of the aircraft is greatly improved.
Description
technical field [0001] The invention relates to the technical field of hypersonic vehicle aerodynamic shape design, in particular to a hypersonic vehicle design method and system. Background technique [0002] In conventional hypersonic vehicles, most of them are similar to the configuration of waveriders to achieve high lift-to-drag ratio characteristics under hypersonic flight conditions. It is an ideal aerodynamic configuration for hypersonic vehicles, but conventional waveriders are flat , the volume is small, and the loading capacity is not ideal. Conventional hypersonic engines are generally embedded in the fuselage, especially the combustion chamber is placed inside the fuselage. Therefore, a large S-bend isolation section is required to connect the air inlet and the combustion chamber in the layout of a conventional superb aircraft, and the large S-bend isolation section produces a huge internal resistance. In addition, for a hypersonic vehicle whose main configura...
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IPC IPC(8): B64F5/00B64C30/00
CPCB64C30/00B64F5/00
Inventor 丁峰张文浩柳军陈韶华蒋浩周芸帆于红恩
Owner NAT UNIV OF DEFENSE TECH